Combustion chamber module for an aircraft turbine engine comprising marks facilitating identification during endoscopic inspection of the combustion chamber

Abstract

The invention relates to a combustion chamber module for an aircraft turbine engine, comprising a combustion chamber defined by an internal annular wall and an external annular wall provided with air intake openings, the module further comprising an internal housing and an external housing. According to the invention, at least one of the internal and external housings has, on the surface thereof facing the combustion chamber, a marking system comprising a plurality of different marks angularly spaced apart from each other, each mark being produced facing one of the air intake openings in order to be visible from inside the combustion chamber and each indicating the angular position of a zone of the combustion chamber comprising the air intake opening.

What is claimed is: 
     
       1. Combustion chamber module for an aircraft turbine engine, comprising a combustion chamber defined by an inner annular wall and an outer annular wall provided with air inlet orifices, said module also comprising an inner casing as well as an outer casing between which the inner and outer annular walls are arranged,
 wherein at least one of the inner and outer casings has, on a surface facing the combustion chamber, a marking system comprising a plurality of different marks angularly spaced apart from each other, each mark being made facing one of the air inlet orifices in order to be visible from an inside of the combustion chamber, and each informing on an angular position of a zone of the combustion chamber comprising said air inlet orifice. 
 
     
     
       2. Combustion chamber module according to  claim 1 , wherein the marks are numbers and/or letters. 
     
     
       3. Combustion chamber module according to  claim 1 , wherein the chamber is also defined by a chamber endwall provided with a plurality of fuel-injection devices in succession in a circumferential direction of the chamber, and in that a number of the marks is identical to a number of the fuel-injection devices. 
     
     
       4. Combustion chamber module according to  claim 1 , wherein the marks are made radially facing the air inlet orifices. 
     
     
       5. Combustion chamber module according to  claim 4 , wherein the air inlet orifices comprise primary orifices and/or dilution orifices. 
     
     
       6. Method for endoscopic inspection of a combustion chamber of a module according to  claim 1 , the method comprising the following successive steps:
 inserting an endoscope into the combustion chamber; 
 performing an indirect visual check of the combustion chamber using the endoscope; and 
 recording at least one image of the combustion chamber while associating with this image an angular position using at least one of the marks present on the inner and outer casing(s) of the combustion chamber module. 
 
     
     
       7. Inspection method according to  claim 6 , wherein said association of the mark with the image is carried out:
 by making the mark visible on the recorded image, and/or 
 by identifying before or after the recording of the image, using the endoscope, the mark of the zone of the combustion chamber corresponding to said image. 
 
     
     
       8. Combustion chamber module according to  claim 1 , wherein the marks are arranged around the combustion chamber in a circumferential direction. 
     
     
       9. Aircraft turbine engine including a combustion chamber module comprising:
 a combustion chamber defined by an inner annular wall and an outer annular wall provided with air inlet orifices, said module also comprising an inner casing as well as an outer casing between which the inner and outer annular walls are arranged, 
 wherein at least one of the inner and outer casings has, on a surface facing the combustion chamber, a marking system comprising a plurality of different marks angularly spaced apart from each other, each mark being made facing one of the air inlet orifices in order to be visible from the inside of the combustion chamber, and each informing on the angular position of a zone of the combustion chamber comprising said air inlet orifice.